Federal Register / Vol. 75, No. 133 / Tuesday, July 13, 2010 / Rules and Regulations 39803 

accordance with 5 U.S.C. 552(a) and 1 CFR 

part 51. Contact McCauley Propeller Systems, 

P.O. Box 7704, Wichita, KS 67277–7704; 

telephone (800) 621–7767, for a copy of this 

service information. You may review copies 

at the FAA, New England Region, 12 New 

England Executive Park, Burlington, MA; or 

at the National Archives and Records 

Administration (NARA). For information on 

the availability of this material at NARA, call 

202–741–6030, or go to: http:// 

www.archives.gov/federal-register/cfr/ibrlocations.html. 

Issued in Burlington, Massachusetts, on 

July 1, 2010. 

Francis A. Favara, 

Manager, Engine and Propeller Directorate, 

Aircraft Certification Service. 

[FR Doc. 2010–16615 Filed 7–12–10; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2010–0308; Directorate 

Identifier 2010–NE–17–AD; Amendment 39– 

16366; AD 2010–14–21] 

RIN 2120–AA64 

Airworthiness Directives; Thielert 

Aircraft Engines GmbH Model TAE 

125–01 Reciprocating Engines 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Final rule. 

SUMMARY: We are adopting a new 

airworthiness directive (AD) for the 

products listed above. This AD results 

from mandatory continuing 

airworthiness information (MCAI) 

issued by an aviation authority of 

another country to identify and correct 

an unsafe condition on an aviation 

product. The MCAI describes the unsafe 

condition as: 

Service has shown that the small outlet of 

the blow-by oil separators, part number 02– 

7250–18100R1; 02–7250–18100R2; 02–7250– 

18100R3; 02–7250–18100R4; 02–7250– 

18300R1; 02–7250–18300R2; 02–7250– 

18300R3; 02–7250–18300R4; or 02–7250– 

18300R5, may cause a blow-by gas pressure 

increase inside the crankcase of the engine in 

excess of the oil seal design pressure limits. 

Leaking engine oil may adversely affect the 

gearbox clutch or the engine lubrication 

system. This condition, if not corrected, 

could lead to in-flight cases of engine power 

loss or ultimately, shutdown. 

We are issuing this AD to prevent loss 

of engine power or uncommanded 

engine shutdown during flight due to 

excessive crankcase blow-by gas 

pressure. 

DATES: This AD becomes effective 

August 17, 2010. The Director of the 

Federal Register approved the 

incorporation by reference of certain 

publications listed in this AD as of 

August 17, 2010. 

ADDRESSES: The Docket Operations 

office is located at Docket Management 

Facility, U.S. Department of 

Transportation, 1200 New Jersey 

Avenue SE., West Building Ground 

Floor, Room W12–140, Washington, DC 

20590–0001. 

FOR FURTHER INFORMATION CONTACT: Tara 

Chaidez, Aerospace Engineer, Engine 

Certification Office, FAA, Engine and 

Propeller Directorate, 12 New England 

Executive Park, Burlington, MA 01803; 

e-mail: tara.chaidez@faa.gov; telephone 

(781) 238–7773; fax (781) 238–7199. 

SUPPLEMENTARY INFORMATION: 

Discussion 

We issued a notice of proposed 

rulemaking (NPRM) to amend 14 CFR 

part 39 to include an AD that would 

apply to the specified products. That 

NPRM was published in the Federal 

Register on April 5, 2010 (75 FR 17084). 

That NPRM proposed to correct an 

unsafe condition for the specified 

products. The MCAI states that: 

Service has shown that the small outlet of 

the blow-by separators, part number 02– 

7250–18100R1; 02–7250–18100R2; 02–7250– 

18100R3; 02–7250–18100R4; 02–7250– 

18300R1; 02–7250–18300R2; 02–7250– 

18300R3; 02–7250–18300R4; or 02–7250– 

18300R5, may cause a blow-by gas pressure 

increase inside the crankcase of the engine in 

excess of the oil seal design pressure limits. 

Leaking engine oil may adversely affect the 

gearbox clutch or the engine lubrication 

system. This condition, if not corrected, 

could lead to in-flight cases of engine power 

loss or ultimately, shutdown. 

Comments 

We gave the public the opportunity to 

participate in developing this AD. We 

received no comments on the NPRM or 

on the determination of the cost to the 

public. 

Conclusion 

We reviewed the available data and 

determined that air safety and the 

public interest require adopting the AD 

as proposed. 

Costs of Compliance 

Based on the service information, we 

estimate that this AD will affect about 

250 Thielert Aircraft Engines GmbH 

model TAE 125–01 engines installed on 

airplanes of U.S. registry. We also 

estimate that it will take about 1.5 workhours per engine to comply with this 

AD. The average labor rate is $85 per 

work-hour. Required parts will cost 

about $1,500 per engine. Based on these 

figures, we estimate the cost of the AD 

on U.S. operators to be $406,875. 

Authority for This Rulemaking 

Title 49 of the United States Code 

specifies the FAA’s authority to issue 

rules on aviation safety. Subtitle I, 

section 106, describes the authority of 

the FAA Administrator. ‘‘Subtitle VII: 

Aviation Programs,’’ describes in more 

detail the scope of the Agency’s 

authority. 

We are issuing this rulemaking under 

the authority described in ‘‘Subtitle VII, 

Part A, Subpart III, Section 44701: 

General requirements.’’ Under that 

section, Congress charges the FAA with 

promoting safe flight of civil aircraft in 

air commerce by prescribing regulations 

for practices, methods, and procedures 

the Administrator finds necessary for 

safety in air commerce. This regulation 

is within the scope of that authority 

because it addresses an unsafe condition 

that is likely to exist or develop on 

products identified in this rulemaking 

action. 

Regulatory Findings 

We determined that this AD will not 

have federalism implications under 

Executive Order 13132. This AD will 

not have a substantial direct effect on 

the States, on the relationship between 

the national government and the States, 

or on the distribution of power and 

responsibilities among the various 

levels of government. 

For the reasons discussed above, I 

certify this AD: 

1. Is not a ‘‘significant regulatory 

action’’ under Executive Order 12866; 

2. Is not a ‘‘significant rule’’ under the 

DOT Regulatory Policies and Procedures 

(44 FR 11034, February 26, 1979); and 

3. Will not have a significant 

economic impact, positive or negative, 

on a substantial number of small entities 

under the criteria of the Regulatory 

Flexibility Act. 

We prepared a regulatory evaluation 

of the estimated costs to comply with 

this AD and placed it in the AD docket. 

Examining the AD Docket 

You may examine the AD docket on 

the Internet at http:// 

www.regulations.gov; or in person at the 

Docket Operations office between 9 a.m. 

and 5 p.m., Monday through Friday, 

except Federal holidays. The AD docket 

contains this AD, the regulatory 

evaluation, any comments received, and 

other information. The street address for 

the Docket Operations office (phone 

(800) 647–5527) is provided in the 

ADDRESSES section. Comments will be 


jlentini on DSKJ8SOYB1PROD with RULES
39804 Federal Register / Vol. 75, No. 133 / Tuesday, July 13, 2010 / Rules and Regulations 

available in the AD docket shortly after 

receipt. 

List of Subjects in 14 CFR Part 39 

Air transportation, Aircraft, Aviation 

safety, Incorporation by reference, 

Safety. 

Adoption of the Amendment 

■ Accordingly, under the authority 

delegated to me by the Administrator, 

the FAA amends 14 CFR part 39 as 

follows: 

PART 39—AIRWORTHINESS 

DIRECTIVES 

■ 1. The authority citation for part 39 

continues to read as follows: 

Authority: 49 U.S.C. 106(g), 40113, 44701. 

§ 39.13 [Amended] 

■ 2. The FAA amends § 39.13 by adding 

the following new AD: 

2010–14–21 Thielert Aircraft Engines 

GmbH: Amendment 39–16366. Docket 

No. FAA–2010–0308; Directorate 

Identifier 2010–NE–17–AD. 

Effective Date 

(a) This airworthiness directive (AD) 

becomes effective August 17, 2010. 

Affected ADs 

(b) None. 

Applicability 

(c) This AD applies to Thielert Aircraft 

Engines GmbH model TAE 125–01 

reciprocating engines with any of the 

following part number blow-by oil separators 

installed: 

TABLE 1—PART NUMBERS OF AFFECTED BLOW-BY OIL SEPARATORS

02–7250–18100R1 02–7250–18100R2 02–7250–18100R3 

02–7250–18100R4 02–7250–18300R1 02–7250–18300R2 

02–7250–18300R3 02–7250–18300R4 02–7250–18300R5 

These engines are installed in, but not 

limited to, Diamond Aircraft Industries 

Model DA 40, Piper PA–28–161 

(Supplemental Type Certificate (STC) No. 

SA03303AT), and Cessna 172 (STC No. 

SA01303WI) airplanes. 

Reason 

(d) Service has shown that the small outlet 

of the blow-by oil separators, part number 

02–7250–18100R1; 02–7250–18100R2; 02– 

7250–18100R3; 02–7250–18100R4; 02–7250– 

18300R1; 02–7250–18300R2; 02–7250– 

18300R3; 02–7250–18300R4; or 02–7250– 

18300R5, may cause a blow-by gas pressure 

increase inside the crankcase of the engine in 

excess of the oil seal design pressure limits. 

Leaking engine oil may adversely affect the 

gearbox clutch or the engine lubrication 

system. This condition, if not corrected, 

could lead to in-flight cases of engine power 

loss or ultimately, shutdown. 

This AD results from mandatory 

continuing airworthiness information (MCAI) 

issued by an aviation authority of another 

country to identify and correct an unsafe 

condition on an aviation product. We are 

issuing this AD to prevent loss of engine 

power or uncommanded engine shutdown 

during flight due to excessive crankcase 

blow-by gas pressure. 

Actions and Compliance 

(e) Unless already done, do the following 

actions: 

(1) Remove the blow-by oil separators 

listed by part number in Table 1 of this AD 

within the next 110 flight hours after the 

effective date of this AD. 

(2) Use the Measures section of Thielert 

Aircraft Engines GmbH Service Bulletin No. 

TM TAE 125–0019, Revision 1, dated March 

5, 2009, to do the removal from service. 

FAA AD Differences 

(f) None. 

Alternative Methods of Compliance 

(AMOCs) 

(g) The Manager, Engine Certification 

Office, FAA, has the authority to approve 

AMOCs for this AD, if requested using the 

procedures found in 14 CFR 39.19. 

Related Information 

(h) Refer to European Aviation Safety 

Agency AD 2010–0020, dated February 8, 

2010, for related information. 

(i) Contact Tara Chaidez, Aerospace 

Engineer, Engine Certification Office, FAA, 

Engine and Propeller Directorate, 12 New 

England Executive Park, Burlington, MA 

01803; e-mail: tara.chaidez@faa.gov; 

telephone (781) 238–7773; fax (781) 238– 

7199, for more information about this AD. 

Material Incorporated by Reference 

(j) You must use Thielert Aircraft Engines 

GmbH Service Bulletin No. TM TAE 125– 

0019, Revision 1, dated March 5, 2009, to do 

the actions required by this AD, unless the 

AD specifies otherwise. 

(1) The Director of the Federal Register 

approved the incorporation by reference of 

this service information under 5 U.S.C. 

552(a) and 1 CFR part 51. 

(2) For service information identified in 

this AD, contact Thielert Aircraft Engines 

GmbH, Platanenstrasse 14 D–09350, 

Lichtenstein, Germany, telephone: +49– 

37204–696–0; fax: +49–37204–696- 55; email: info@centurion-engines.com. 

(3) You may review copies at the FAA, 

New England Region, 12 New England 

Executive Park, Burlington, MA; or at the 

National Archives and Records 

Administration (NARA). For information on 

the availability of this material at NARA, call 

(202) 741–6030, or go to: http:// 

www.archives.gov/federal-register/cfr/ibrlocations.html. 

Issued in Burlington, Massachusetts, on 

July 1, 2010. 

Francis A. Favara, 

Manager, Engine and Propeller Directorate, 

Aircraft Certification Service. 

[FR Doc. 2010–16618 Filed 7–12–10; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2008–0274; Directorate 

Identifier 2008–NM–038–AD; Amendment 

39–16367; AD 2010–15–01] 

RIN 2120–AA64 

Airworthiness Directives; The Boeing 

Company Model 757 Airplanes, Model 

767 Airplanes, and Model 777–200 and 

–300 Series Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Final rule. 

SUMMARY: We are adopting a new 

airworthiness directive (AD) for certain 

Model 757 airplanes, Model 767 

airplanes, and Model 777–200 and –300 

series airplanes. This AD requires 

repetitive inspections for damage of the 

electrical terminal at the left and right 

flightdeck window 1, and corrective 

actions if necessary. This AD also 

allows for replacing the flightdeck 

window 1 with a new improved 

flightdeck window equipped with 

different electrical connections, which 

terminates the repetitive inspections for 

that flightdeck window 1. This AD 

results from several reports of electrical 

arcs at the terminal blocks of the 

electrically heated flightdeck window 1. 

We are issuing this AD to prevent smoke 

and fire in the cockpit, which could 

lead to loss of visibility, and injuries to 

or incapacitation of the flightcrew. 

DATES: This AD is effective August 17, 

2010. 

The Director of the Federal Register 

approved the incorporation by reference 

of certain publications listed in the AD 

as of August 17, 2010. 


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